US 12,442,309 B2
Nozzle assembly for turbine engine
Paul Hadley Vitt, Liberty Township, OH (US); Wilson Frost, Cincinnati, OH (US); and Mark Broomer, Lynn, MA (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Sep. 12, 2019, as Appl. No. 16/568,730.
Prior Publication US 2021/0079799 A1, Mar. 18, 2021
Int. Cl. F01D 9/04 (2006.01)
CPC F01D 9/042 (2013.01) [F05D 2220/32 (2013.01); F05D 2240/128 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A nozzle assembly for a turbine engine, the nozzle assembly comprising:
an outer band;
an inner band spaced from the outer band;
a first airfoil extending between the outer band and the inner band, extending between a leading edge and a trailing edge, and including a first pressure side and a first suction side;
a second airfoil extending between the outer band and the inner band and spaced from the first airfoil and including a second pressure side and a second suction side;
a throat defined as a minimum cross-sectional area between the first airfoil and the second airfoil extending between the trailing edge of the first airfoil and the second suction side of the second airfoil;
additional material provided at the throat, with the additional material provided on at least a portion of one of the inner band or the outer band; and
a formed portion positioned in the additional material at the throat with a central portion of the formed portion aligned at the throat;
wherein the central portion defines a maximum cross-sectional distance for the formed portion arranged at the throat.